KR101768325B1 - Drone and charging system comprising for drone - Google Patents

Drone and charging system comprising for drone Download PDF

Info

Publication number
KR101768325B1
KR101768325B1 KR1020150133590A KR20150133590A KR101768325B1 KR 101768325 B1 KR101768325 B1 KR 101768325B1 KR 1020150133590 A KR1020150133590 A KR 1020150133590A KR 20150133590 A KR20150133590 A KR 20150133590A KR 101768325 B1 KR101768325 B1 KR 101768325B1
Authority
KR
South Korea
Prior art keywords
terminal
charging device
air
airplane
negative terminal
Prior art date
Application number
KR1020150133590A
Other languages
Korean (ko)
Other versions
KR20170035042A (en
Inventor
이선호
Original Assignee
한국항공우주연구원
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 한국항공우주연구원 filed Critical 한국항공우주연구원
Priority to KR1020150133590A priority Critical patent/KR101768325B1/en
Publication of KR20170035042A publication Critical patent/KR20170035042A/en
Application granted granted Critical
Publication of KR101768325B1 publication Critical patent/KR101768325B1/en

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/08—Helicopters with two or more rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
    • B64D35/02—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions specially adapted for specific power plants
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F1/00—Ground or aircraft-carrier-deck installations
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0042—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries characterised by the mechanical construction
    • H02J7/0044—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries characterised by the mechanical construction specially adapted for holding portable devices containing batteries
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J7/00—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries
    • H02J7/0042—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries characterised by the mechanical construction
    • H02J7/0045—Circuit arrangements for charging or depolarising batteries or for supplying loads from batteries characterised by the mechanical construction concerning the insertion or the connection of the batteries
    • B64C2201/042—
    • B64C2201/066—

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Power Engineering (AREA)
  • Charge And Discharge Circuits For Batteries Or The Like (AREA)
  • Electric Propulsion And Braking For Vehicles (AREA)

Abstract

According to an embodiment of the present invention, there is provided a flight vehicle comprising: a support; a body of the air vehicle provided on the support; a propulsion unit provided on the outer side of the support to generate thrust; a charge battery provided inside the air body; And the air electrode terminal and the air electrode terminal of the airplane body which are connected to each other by the air bag elastic element and separated from the air bag body or the support member from the lower side of the air bag body or the support, And may include a cover that can be protected.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a charging system,

The following embodiments are directed to a rechargeable air vehicle and a flight recharging system including the same.

Drone, which started in the military industry, refers to an airplane or helicopter-shaped airplane flying by induction of radio waves without human being. Recently, it has been widely used military and commercial by using the above-mentioned airplane. It is progressing.

Generally, a flying body is equipped with a rechargeable battery such as a battery, and in order to charge the rechargeable battery, the flight is stopped and power is applied to the flying body to charge the rechargeable battery.

In addition, because of the limit of energy capacity relative to the weight of the battery, the flight time can be in the range of 10 to 20 minutes. For aircraft that monitor / observe around a certain area, continuous battery replacement work is required for continuous operation.

That is, when a plurality of air vehicles are operated at the same time, a plurality of air vehicles must be frequently stopped to charge the air vehicles. In addition, since the charging device is connected to the airplane to charge the airplane, it is difficult to charge the airplane when the airplane is operated simultaneously.

Korean Patent Registration No. 1160096 discloses a charging device for charging a motor vehicle to charge a power source through the charging device.

An object according to an embodiment is to provide a flight body having a configuration including a cover that can protect the charging terminal from external shock, friction, and contamination without exposing the charging terminal to the outside.

An object of the present invention is to provide a charging device which can be installed over a wide area such as a charging station dedicated to a flight, a roof of a building, a telephone pole, a streetlight, and a moving vehicle.

Also, an object according to an embodiment is to provide a flight object charging system capable of constituting a flight device and a charging device including a landing pad capable of protecting a charging device anode terminal and a charging device anode terminal from external shock, friction, .

According to an embodiment of the present invention, there is provided a flight vehicle comprising: a support; a body of the air vehicle provided on the support; a propulsion unit provided on the outer side of the support to generate thrust; a charge battery provided inside the air body; And the air electrode terminal and the air electrode terminal of the airplane body which are connected to each other by the air bag elastic element and separated from the air bag body or the support member from the lower side of the air bag body or the support, And may include a cover that can be protected.

A plurality of openings formed at a position corresponding to the air body positive terminal and the air negative terminal of the air body are formed on the lower side of the air body main body, Wherein the air body positive terminal and the air negative terminal are exposed through the plurality of openings when the flight elastic element is contracted.

Wherein the air electrode terminal and the air electrode terminal are provided in a groove formed in the air body body and the cover is formed on the lower side of the air body body and extends to the upper side of the cover at a position corresponding to the air battery cathode terminal and the air- The air electrode terminal and the air electrode negative terminal may be in contact with the plurality of conductor elements when the flight elastic element is contracted.

Wherein the air electrode terminal and the air electrode terminal of the airplane part protrude downward from a portion of the support member which extends downwardly from the support member and the cover is formed below a portion of the support member extending downwardly, And a plurality of openings formed at positions corresponding to the air electrode negative terminal, wherein the air electrode terminal and the air electrode negative terminal are exposed through the plurality of openings when the flight elastic element is contracted.

Wherein the air electrode terminal and the air electrode terminal are provided in a groove formed in a portion extending downward from the support member and the cover is formed below a portion extending downward from the support member, And a plurality of conductor elements extending upward from the cover at positions corresponding to the negative terminal, wherein the air electrode terminal and the air electrode negative terminal are in contact with the plurality of conductor elements when the flight elastic element is contracted .

In addition, the flight elastic element may be spring-shaped.

The airborne filling system according to an embodiment may include a flying object including a power source that can be charged, and a charging device that supplies power to the power source.

The power source may be connected to the charging device when the flying object is docked to the charging device. When the flying object is not docked to the charging device, the power source may be protected by the cover provided on the airplane .

The charging device includes a charging device main body, a power battery provided inside the charging device main body, a charging device anode terminal connected to the power battery and provided in the charging device main body, a charging device negative terminal, And a landing pad spaced apart from the main body of the charging device and connected to the charging device elastic element to protect the charging device positive terminal and the charging device negative terminal.

The landing pad first conductor being formed at a position corresponding to the charging device anode terminal and the charging device cathode terminal, and the landing pad first conductor being formed at a position corresponding to the charging device anode terminal and the charging device anode terminal, The landing pad second conductor, wherein the filling device positive terminal and the filling device negative terminal may be in contact with the landing pad first conductor and the landing pad second conductor when the filling device elastic element is contracted.

Any one of the charging device positive terminal and the charging device negative terminal may be provided at the center of the upper surface of the charging device body and the other terminal may be provided at the upper surface edge of the charging device body.

In addition, among the landing pad first conductor or the landing pad second conductor, a terminal corresponding to a terminal provided at the center of the top surface of the filling apparatus main body is provided at the center of the landing pad, May be provided on the edge. The landing pad first conductor and the landing pad second conductor may be partitioned by an insulator.

Wherein the power source unit of the airplane includes a positive electrode terminal of the airplane body and a negative electrode terminal of the airplane body and either one of the positive electrode terminal of the airplane body or the negative electrode terminal of the airplane body is partially protruded at the center of the lower surface of the airplane body, And the other terminal may be provided in a state where a part of the terminal protrudes from the bottom edge of the air body.

The cover includes a plurality of openings formed on the lower side of the air body and spaced apart from the body of the air body and connected to the air body by a flight elastic element and formed at positions corresponding to the air body positive terminal and the air body negative terminal can do.

When the flying object is docked to the charging device, the flying element positive terminal and the flying object negative terminal may be contracted and exposed through the plurality of openings.

The power source unit includes a positive electrode terminal of the airplane body and a negative electrode terminal of the airplane body. One of the positive electrode terminal and the negative electrode terminal of the airplane body is provided in a groove formed at the center of the lower surface of the airplane body, The terminal may be provided in a groove formed in the lower edge of the air body.

The cover is spaced apart from the body of the airplane at a lower side of the airplane body and connected to the airplane body by an elastic element of the airplane, and extends to the upper side of the cover at a position corresponding to the airplane positive terminal and the airplane negative terminal And may include a plurality of formed conductive elements.

When the flying object is docked to the charging device, the flight elastic element is contracted and brought into contact with the plurality of conductive elements.

The air vehicle according to one embodiment may include a cover that can protect the charging terminal from external impact, friction, contamination, etc. without exposing the charging terminal to the outside.

The charging apparatus according to one embodiment may be installed over a wide area such as a charging station dedicated to a flight, a building roof, a telephone pole, a streetlight, a moving vehicle, and the like.

In addition, the airborne filling system according to one embodiment can protect the positive and negative terminals used for filling the air vehicle from external impact, friction, dirt, etc. by including the cover of the airborne and the landing pad of the filling device.

1 to 4 show a flying body according to an embodiment including a cover that can protect a terminal of a power source unit.
5 shows a charging apparatus of a flight filling system.
Fig. 6 shows an enlarged view of the landing pad portion of the filling apparatus in Fig.
7 shows a state before the air vehicle and the charging device are docked.
8 shows a state in which a flying object and a charging device are docked.

Hereinafter, embodiments will be described in detail with reference to the accompanying drawings. The following description is one of many aspects of the embodiments and the following description forms part of a detailed description of the embodiments.

In the following description, well-known functions or constructions are not described in detail to avoid unnecessarily obscuring the subject matter of the present invention.

In addition, terms and words used in the present specification and claims should not be construed in a conventional or dictionary sense, and the inventor shall design his /

It should be construed as meaning and concept consistent with the technological idea of the air vehicle according to the embodiment on the principle that the concept of the term can be appropriately defined in order to explain it by a method.

Therefore, the embodiment described in the present specification and the configuration shown in the drawings are merely the most preferred embodiment of the air vehicle according to the embodiment, and not all of the technical ideas of the air vehicle according to the embodiment are described. It should be understood that various equivalents and modifications may be substituted for those at a later point in time.

FIGS. 1 to 4 show a flying body according to an embodiment including a cover for protecting a terminal of a power source unit, and FIG. 5 shows a charging apparatus of a flight filling system. FIG. 6 shows an enlarged view of the landing pad portion of the filling apparatus in FIG. 5, and FIG. 7 shows a state before the flying body and the filling apparatus are docked. 8 shows a state in which a flying object and a charging device are docked.

1 to 4, the air vehicle 100 according to one embodiment includes a support body 110, a flight body 120 provided on the support body 110, and a support body 110, A charging battery 140 provided inside the body 120 of the airplane body and a body terminal 151 of the airplane body connected to the charging battery 140 and provided in the body 120 or the support 110, And a flying body negative terminal 152.

The flight body elastic member 160 is connected to the air body 120 or the support member 110 by the air body elastic member 160 at a lower side of the air body 120 or the support member 110 from the air body 120 or the support member 110 And a cover 170 that can protect the air body positive terminal 151 and the air vehicle negative terminal 152. [

The support base 110 may be formed as a frame, and in one embodiment, the support base 110 is formed in an 'X' shape. However, the support base 110 is not limited to this shape, but may be formed in any shape such as '?' .

The air body 120 has a cylindrical shape, but is not limited thereto, and may be formed in any shape, such as a hexahedron shape, a triangular pyramid shape, or an octahedral shape, if necessary.

The air vehicle 100 may further include a propelling unit 130. The propelling unit 130 may include a propelling element 132 for generating a thrust and a driving element 131 for generating and transmitting a driving force to the propelling element 132.

The propulsion unit 130 generates a thrust force to perform an operation (flying, landing, or landing) of the air vehicle 100. Although it is recommended that the propelling unit 132 uses a thrust generated by rotation of a propeller widely used in the air vehicle 100, it is possible to implement various propelling elements 132 such as a jet engine in addition to the propeller method. It is not limited to the propeller method.

In addition, although the octrotor is described as an example for convenience, the present invention can be implemented in various shapes such as a tri-rotor, a quadrature rotor, a penta rotor, a hex rotor, an octrotor, and the like regardless of the number and configuration of the propelling elements 132.

A charging battery 140 may be provided inside the air body 120. However, the charging battery 140 is not necessarily limited to the inside of the air body 120, and it may be provided outside the air body 120 if necessary.

One aviation positive terminal 151 is positioned at the center of the lower surface of the aircraft body 120 and two aviation negative terminals 152 are positioned at the lower edge of the aircraft body 120. However, the number of the positive electrode terminal 151 and the negative electrode terminal 152 of the aircraft body may be changed as necessary.

It is obvious that the positions to be installed can also be provided at positions opposite to each other and at the third different position. This is the same in the embodiment described below.

1, one avionic terminal 151 and two aviation negative terminals 152 are connected to the rechargeable battery 140 and the avionic terminal 151 is connected to the bottom of the aviation body 120 And a part protruding from the center of the surface. In addition, the air electrode negative terminal 152 may be partially protruded from the bottom edge of the air body 120.

The cover 170 is separated from the air body 120 on the lower side of the air body 120 and is connected to the air body 120 by the air elastic element 160. The cover 170 is connected to the air body positive terminal 151 and the air body negative terminal (152).

That is, the cover 170 is provided below the air body 120 so that the air electrode terminal 151 and the air electrode negative terminal 152 protruding from the lower surface of the air body 120 are not exposed to the outside The air electrode terminal 151 and the air electrode terminal 152 can be protected from external impact, friction, dirt, and the like.

The cover 170 may include a plurality of openings 180 formed at positions corresponding to the air body positive terminal 151 and the air vehicle negative terminal 152. That is, one opening 180 may be formed at the center of the cover 170 in correspondence with one flight body anode terminal 151 located at the center of the lower surface of the air body 120. In addition, two openings 180 may be formed at the edge of the cover 170 corresponding to the two air vehicle negative electrode terminals 152 located at the lower edge of the air body 120. However, as described above, the number or installation positions of the air body positive terminal 151 and the air body negative terminal 152 can be changed flexibly as required. Accordingly, the opening 180 ) Or the position in which it is formed can also be changed in a fluid manner. This is the same in the embodiment described below.

When the flying body 100 is landed and docked on the filling apparatus 200 to be described later, the flying body elastic element 160 is contracted by the weight of the flying body 100. At this time, the flying body positive terminal 151 and the flying body negative terminal The opening 152 may be exposed to the outside through the plurality of openings 180. [

Hereinafter, the installation position and the role of the cover 170 described above will be omitted in order to avoid repetitive unnecessary descriptions, and differences will be mainly described.

Referring to FIG. 2, according to a modified embodiment of the air vehicle body 100, one air vehicle body cathode terminal 151 may be provided in a groove formed at the center of the lower surface of the air body 120. In addition, two air vehicle negative electrode terminals 152 may be provided in a groove formed in the lower edge of the body 120 of the air body.

2 (a), the cover 170 is formed at a position corresponding to the flying body positive terminal 151 and the flying body negative terminal 152, (Not shown).

 In other words, one conductor element 190 may be formed at the center of the cover 170 corresponding to one aviation body positive terminal 151 located at the center of the lower surface of the air body 120. In addition, two conductive elements 190 may be formed at the edge of the cover 170 corresponding to the two air vehicle negative electrode terminals 152 located at the lower edge of the body 120 of the air vehicle body. However, as described above, the number or installation positions of the air-fuel-cell positive electrode terminal 151 and the air-vehicle negative electrode terminal 152 can be changed flexibly as required. 190 or the position in which it is formed can also be changed in a fluid manner. This is the same in the embodiment described below.

2 (b), when the air vehicle 100 is landed and docked on the filling device 200 to be described later, the flying elastic element 160 is contracted by the weight of the air vehicle 100, The anode terminal 151 and the air electrode cathode terminal 152 may be in contact with the plurality of conductive elements 190.

It will be apparent to those skilled in the art that the conductor elements can be replaced with elements having the properties of a cathode or a cathode, if necessary.

3, the airplane positive terminal 151 and the airplane negative terminal 152 are connected to the rechargeable battery 140 and extend to the lower side of the supporter 110 And may protrude downward from the formed portion 111.

3 (a), the cover 170 is spaced apart from the support base 110 below the portion 111 extending downward from the support base 110, and is supported by the flight- (110), and can protect the airplane positive terminal (151) and the air vehicle negative terminal (152).

The cover 170 may include a plurality of openings 180 formed at positions corresponding to the air body positive terminal 151 and the air vehicle negative terminal 152. The openings 180 may be formed in the cover 170 in correspondence with the air body positive terminal 151 and the air body negative terminal 152 located in the portion 111 extending downward from the support base 110 .

3 (b), when the air vehicle 100 is landed and docked on the filling device 200, which will be described later, the flight vehicle elastic element 160 is contracted due to the weight of the air vehicle 100, The positive electrode terminal 151 and the air electrode negative terminal 152 can be exposed to the outside through the opening 180.

4, according to another modified embodiment of the air vehicle body 100, the air body positive terminal 151 and the air vehicle negative terminal 152 are connected to the rechargeable battery 140 and extend downwardly of the support 110 And may be provided in a groove formed under the formed portion 111.

4A, the cover 170 is spaced apart from the support base 110 below the portion 111 extending downward from the support base 110, and is supported by the flight- (110), and can protect the airplane positive terminal (151) and the air vehicle negative terminal (152).

The cover 170 is formed at a position corresponding to the flying body positive terminal 151 and the flying body negative terminal 152 located in the groove formed in the portion 111 extending downward from the support base 110, And a plurality of conductive elements 190 formed to extend upward from the upper surface of the base body 110.

4 (b), when the air vehicle 100 is landed and docked on the charging device 200 to be described later, the flying elastic element 160 is contracted due to the weight of the air vehicle 100, The terminal 151 and the air electrode negative terminal 152 may be in contact with the plurality of conductive elements 190.

The charging battery 140 is provided inside the driving element 131 and the air electrode terminal 151 and the air electrode terminal 152 are connected to the charging battery 140 and protruded below the driving element 131 .

The cover 170 is separated from the driving element 131 on the lower side of the driving element 131 and connected to the driving element 131 by the flight elastic element 160, The terminal 152 can be protected.

The cover 170 may include a plurality of openings 180 formed at positions corresponding to the air body positive terminal 151 and the air vehicle negative terminal 152. The openings 180 may be formed in the cover 170 in correspondence with the air electrode terminal 151 and the air electrode negative terminal 152 located at the driving element 131, respectively.

When the flying body 100 is landed and docked on the filling apparatus 200 to be described later, the flying body elastic element 160 is contracted by the weight of the flying body 100. At this time, the flying body positive terminal 151 and the flying body negative terminal The opening 152 may be exposed to the outside through the opening 180.

In addition, the air body positive terminal 151 and the air body negative terminal 152 may be connected to the rechargeable battery 140 and may be provided in the groove formed below the driving element 131.

The cover 170 is separated from the driving element 131 on the lower side of the driving element 131 and connected to the driving element 131 by the flight elastic element 160, The terminal 152 can be protected.

The cover 170 is formed at a position corresponding to the air electrode positive terminal 151 and the air negative electrode terminal 152 located in the groove formed in the driving element 131 and has a plurality of And may include a conductive element 190.

When the air vehicle 100 is landed and docked on the filling device 200 to be described later, the flying elastic element 160 is contracted due to the weight of the air vehicle 100. At this time, the air vehicle body terminal 151 and the air vehicle negative terminal 152 may be in contact with the plurality of conductive elements 190. The flight elastic element 160 may be spring-shaped. However, in one embodiment, a spring is used as the flight elastic element 160, but it is not necessarily limited thereto, and it is obvious that another elastic material may be used.

Hereinafter, the air vehicle charging system 10 according to an embodiment including the air vehicle 100 will be described. The airborne filling system 10 according to an embodiment may include a flying object 100 including a power source unit 150 that can be charged and a charging device 200 that supplies power to the power source unit 150.

When the air vehicle 100 is docked to the charging apparatus 200, the power source unit may be connected to the charging apparatus 200 and charged. When the air vehicle 100 is not docked to the charging apparatus 200, May be protected by a cover (170) provided on the housing (100).

The operation of the charging device 200 and the air bag charging system 10 will be described below with reference to the air vehicle 100 in detail.

5, the charging apparatus 200 includes a charging apparatus main body 210, a power battery 220 provided inside the charging apparatus main body 210, a power supply battery 220 connected to the charging apparatus main body 210 A charging device anode terminal 231 and a charging device cathode terminal 232 provided in the charging device.

The charging device main body 210 is separated from the charging device main body 210 and connected to the charging device main body 210 by the charging device elastic element 240 so that the charging device positive terminal 231, And a landing pad 250 that can protect the negative terminal 232.

The main body 120 of the charging device 120 may have a cylindrical shape, but is not limited thereto, and may be formed in various shapes such as a square pillar, an octagonal pillar, and the like.

A power supply battery 220 may be provided inside the charging apparatus main body 120 to supply power to the charging battery 140 of the air vehicle 100 when the charging apparatus 200 and the air vehicle body 100 are docked, .

The power supply battery 220 may be supplied with electric power by a power supply unit 260 provided outside the charging apparatus main body 210. The power supply unit 260 may include an external power supply, a gasoline / diesel generator, Generator may be used.

The charging device cathode terminal 231 and the charging device cathode terminal 232 may be formed so that a part thereof protrudes above the charging device body 210. The landing pad 250 is formed so as to surround the charging device positive terminal 231 and the charging device negative terminal 232 on a part of the charging device positive terminal 231 and the charging device negative terminal 232 protruding, The device positive terminal 231 and the charging device negative terminal 232 are not exposed to the outside.

That is, the charging device positive terminal 231 and the charging device negative terminal 232 are located below the landing pad 250, so that they can be protected from external impact, friction, contamination, and the like.

The landing pad 250 also includes a landing pad first conductor 251 and a landing pad second conductor 252 formed at positions corresponding to the charging device anode terminal 231 and the charging device cathode terminal 232 . Thus, when the air vehicle 100 is landed and docked on the charging pad 250, the charging device elastic element 240 is contracted and the charging device anode terminal 231 and the charging device cathode terminal 232 are connected to the landing pad first It may be contacted with the conductor 251 and the landing pad second conductor 252.

One of the charging device positive terminal 231 and the charging device negative terminal 232 is provided at the center of the upper surface of the charging device body 210 and the other terminal is provided at the upper edge of the charging device body 210 .

The landing pad first conductor 251 may be provided at the center of the upper surface of the main body 210 of the filling apparatus and the landing pad second conductor 252 may be provided at the edge of the landing pad 250. The landing pad first conductor 251 and the landing pad second conductor 252 may be partitioned by an insulator.

One charging device anode terminal 231 is provided so as to protrude from the center of the upper surface of the charging device body 210 and two charging device cathode terminals 232 are provided on the top surface of the charging device body 210 And may be provided such that a part thereof protrudes from the edge.

6, a landing pad first conductor 251 is provided at the center of the landing pad 250, and an edge of the landing pad 250 is formed to surround the landing pad first conductor 251, The landing pad second conductor 252 may be provided. The landing pad first conductor 251 and the landing pad second conductor 252 may be partitioned by an insulator 253.

When the air vehicle 100 is landed and docked on the charging pad 250, the charging device elastic element 240 is contracted and the charging device positive terminal 231 is brought into contact with the landing pad first conductor 251 And the charging device cathode terminal 232 may be in contact with the landing pad second conductor 252.

It is obvious that the landing pad 250 may be formed in various shapes such as a triangular plate shape, a rectangular plate shape, a hexagonal plate shape, or the like, but it is not limited thereto.

However, the number or location of the charging device anode terminal 231 and the charging device cathode terminal 232 may be changed flexibly as required. In response to this, the landing pad first conductor 251 of the landing pad 250 And landing pad second conductor 252 are formed can be fluidly changed.

That is, when the charging device negative terminal 252 is provided at the center of the upper surface of the charging device main body 210 and the charging device positive terminal 251 is provided at the upper edge of the charging device main body 210, The pad second conductor 252 will be provided at the center of the landing pad 250 and the landing pad first conductor 251 will be provided at the edge of the landing pad 250.

Hereinafter, the operation of the flight charging system 10 will be described with reference to FIGS. 7 and 8. FIG. The air vehicle charging system 10 may have two operating modes, i.e., a stand-by mode and a charging mode.

7, in the standby mode, the air vehicle 100 is not docked to the charging device 200, and the charging device positive terminal 231 and the charging device negative terminal 232 are connected to the landing pad first conductor 251 And the landing pad second conductor 252, and are not electrically connected. That is, the flying object 100 can not be charged.

8, when the air vehicle 100 is landed on the landing pad 250 of the charging device 200 and is docked, the flight elastic element 160 is contracted and the opening 180 of the cover 170 The positive electrode terminal 151 and the negative electrode terminal 152 are exposed to the outside. The charging device elastic element 240 of the charging device 200 is contracted so that the charging device positive terminal 231 contacts the landing pad first conductor 251 and the charging device negative terminal 232 contacts the landing pad first conductor 251, 2 conductors 252, respectively.

The air electrode terminal 151 exposed to the outside is connected to the landing pad first conductor 251 and the charging device anode terminal 231 in a line and the air electrode terminal 152 is connected to the landing pad second conductor 252 And the charging device cathode terminal 232, so that the air vehicle 100 can be charged.

The charging device positive terminal 231 and the charging device negative terminal 231 for improving the contact force between the charging device negative terminal 231 and the charging device negative terminal 232 and the landing pad first conductor 251 and landing pad second conductor 252, A cushion, a spring, or the like may be added to the second housing 232.

The landing pad 250 can be easily retracted so that the elastic element 160 can be more easily contracted so that the air body positive terminal 151 and the air vehicle negative terminal 152 are easily exposed through the opening 180 of the cover 170. [ A protruding element 270 may be provided on the upper side. Thus, when the flying object 100 is docked to the filling apparatus 200, the resilient element 160 can be easily retracted by the protruding element 270 supporting the cover 170 from below in the upward direction.

(Not shown) capable of supporting the cover 170 from below so that the resilient element 160 can be more easily contracted and the flight cathode terminal 151 and the aircraft cathode terminal 152 are easily exposed. The anode terminal 151 and the anode terminal 152 of the airplane are formed to protrude from the lower surface of the body 120 of the airplane body, A case has been described in which the flying object 100 including the cover 170 is docked to the charging device 200. [

And a cover 170 having a conductive element 190 that is provided in a groove formed in the body 120 of the air body and extends toward the upper side of the cover 170 When the air bag 100 is docked to the charging apparatus 200, the air bag elastic element 160 is contracted so that the conductive element 190 is connected to the air fuel cell anode terminal 151 and the air fuel cell negative electrode terminal 152 Can be contacted.

The airplane negative terminal 151 is connected in line with the conductive element 190, the landing pad first conductor 251 and the charging device positive terminal 231. The airplane negative terminal 152 is connected to the conductive element 190, The landing pad second conductor 252, and the charging device cathode terminal 232, so that the air vehicle 100 can be charged.

And a cover 170 provided so as to protrude below the portion 111 formed by extending the lower portion of the support member 110 and including the air electrode positive terminal 151 and the air electrode negative terminal 152, In the case of the airplane 100, when the airplane 100 is docked to the charging device 200, the airplane elastic element 160 is contracted, and the airplane positive terminal 151 and the airplane negative terminal 152 are exposed to the outside.

At this time, the airplane positive terminal 151 is connected in line with the landing pad first conductor 251 and the charging device positive terminal 231, and the airplane negative terminal 152 is connected to the landing pad second conductor 252, And is connected in series with the negative terminal 232, so that the air vehicle 100 can be charged.

A conductive element 190 which is provided in the groove of the portion 111 formed by extending the lower portion of the support base 110 and which extends toward the upper side of the cover 170, When the air bag 100 is docked to the charging device 200, the air bag elastic element 160 is contracted so that the conductive element 190 is inserted into the air bag terminal 151, And the aviation negative terminal 152. [0050]

The airplane negative terminal 151 is connected in line with the conductive element 190, the landing pad first conductor 251 and the charging device positive terminal 231. The airplane negative terminal 152 is connected to the conductive element 190, The landing pad second conductor 252, and the charging device cathode terminal 232, so that the air vehicle 100 can be charged.

Through the air vehicle 100 and the air bag charging system 10, the air bag 100 can protect the power supply unit 150 from external impact, friction, and contamination without exposing the air bag 100 to the outside.

In addition, the charging device 200 of the air vehicle charging system 10 can be installed over a wide area such as a charging station dedicated to an airplane, a building roof, a telephone pole, a street lamp, and a moving vehicle. Therefore, by allowing the air vehicle 100 to be charged from time to time, the air vehicle 100 can be operated over a long distance.

In addition, by installing a plurality of charging devices 200 in the surveillance area, it is possible to monitor for 24 hours using a plurality of air vehicles 100.

Although the present invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the disclosed embodiments. The present invention is not limited to the above-described embodiments, and various modifications and changes may be made thereto by those skilled in the art to which the present invention belongs. Therefore, the spirit of the present invention should not be construed as being limited to the above-described embodiments, and all of the equivalents or equivalents of the claims, as well as the following claims, are included in the scope of the present invention.

10: Flight Charging System
100: flight vehicle
110: Support
120:
130: propulsion unit
140: Charging battery
150:
151: Aircraft body terminal
152: Aircraft terminal
160: Elastic element of flight
170: cover
180: opening
190: conductor element
200: Charging device
210: Charging device body
220: Power battery
231: Charging device positive terminal
232: charging device negative terminal
240: Charging device Elastic element
250: landing pad
251: landing pad first conductor
252: landing pad second conductor
253: Insulator
260: Power supply unit
270: protruding element

Claims (12)

support fixture;
A flight body provided on the support;
A propulsion unit provided outside the support and generating a thrust;
A charging battery provided inside the air body;
A positive electrode terminal and a flying electrode negative terminal connected to the charging battery and provided on the air body or the support; And
A cover which is spaced apart from the body of the airplane or below the support and is capable of protecting the airplane cathode terminal and the airplane cathode terminal;
Lt; / RTI >
The cover may be spaced apart from the flight body or the support by a flight elastic element,
When the flying object is landed on the charging device and is docked, the flying elastic element is contracted by the weight of the flying object, and the flying object cathode terminal and the flying object negative terminal are exposed to the outside of the cover or contact with the cover, Which can be, airborne.
delete The method according to claim 1,
Wherein a part of the positive electrode terminal of the airplane and the negative electrode terminal of the airplane protrude downward from the airplane body,
Wherein the cover includes a plurality of openings formed in a lower portion of the air body body and formed at positions corresponding to the air body cathode terminal and the air fuel cell negative terminal,
Wherein the air body positive terminal and the air negative terminal are exposed through the plurality of openings when the flight elastic element is contracted.
The method according to claim 1,
The air body positive terminal and the air negative terminal are provided in a groove formed in the air body,
The cover includes a plurality of conductive elements formed on the lower side of the air body and extending upward from the cover at positions corresponding to the air body positive terminal and the air negative terminal,
Wherein the aircraft positive terminal and the aircraft negative terminal are capable of contacting the plurality of conductor elements when the flight elastic element is contracted.
The method according to claim 1,
Wherein the air body positive terminal and the air negative terminal are partially protruded downward from the support,
Wherein the cover includes a plurality of openings formed on a lower side of the support and formed at positions corresponding to the air body positive terminal and the air body negative terminal,
Wherein the air body positive terminal and the air negative terminal are exposed through the plurality of openings when the flight elastic element is contracted.
The method according to claim 1,
Wherein the air body positive terminal and the air body negative terminal are provided in a groove formed in the support,
The cover includes a plurality of conductive elements formed on the lower side of the support and extending upward from the cover at positions corresponding to the air body positive terminal and the air negative terminal,
Wherein the aircraft positive terminal and the aircraft negative terminal are capable of contacting the plurality of conductor elements when the flight elastic element is contracted.
7. The method according to any one of claims 3 to 6,
Wherein the flight elastic element can be spring-shaped.
A flying body including a power source that can be charged; And
A charging device for supplying power to the power supply unit;
Lt; / RTI >
Wherein the charging device comprises:
A charging apparatus body;
A power battery provided inside the charging device body;
A charging device positive terminal and a charging device negative terminal connected to the power battery and provided in the charging device main body; And
A landing pad spaced apart from the main body of the main body of the charging device by a resilient element of the main body and capable of protecting the charging device positive terminal and the charging device negative terminal;
/ RTI >
When the flying object is docked to the charging device, the charging device elastic element is contracted so that the charging device anode terminal and the charging device negative terminal are brought into contact with the landing pad so that the power source part can be connected to the charging device and charged ,
Wherein the power supply unit can be protected by a cover provided on the airplane when the airplane is not docked to the charging apparatus.
delete 9. The method of claim 8,
A part of the positive electrode terminal of the charging device and the negative electrode terminal of the charging device protrude above the charging device body,
Wherein the landing pad includes a landing pad first conductor and a landing pad second conductor formed at positions corresponding to the charging device positive terminal and the charging device negative terminal,
Wherein the charging device positive terminal and the charging device negative terminal are contactable with the landing pad first conductor and the landing pad second conductor when the charging device elastic element is contracted.
11. The method of claim 10,
Among the charging device positive terminal or the charging device negative terminal,
Wherein one of the terminals is provided at the center of the upper surface of the main body of the charging apparatus and the remaining terminal is provided at the upper edge of the main body of the charging apparatus,
Wherein the landing pad first conductor is provided at the center of the upper surface of the main body of the filling device and the landing pad second conductor is provided at an edge of the landing pad and can be partitioned by an insulator.
9. The method of claim 8,
The power supply unit,
A positive electrode terminal of the airplane, and a negative electrode terminal of the airplane,
Wherein the air body positive terminal and the air negative terminal are provided at a lower end of the air vehicle,
The cover
A plurality of openings or a plurality of conductor elements spaced apart from the airplane at a lower side of the airplane and connected to the airplane by an elastic element of the airplane and formed at a position corresponding to the airplane positive terminal and the airplane negative terminal,
The airplane positive electrode terminal and the airplane negative electrode terminal,
Wherein the flight elastic element is retracted to be exposed through the plurality of openings or in contact with the plurality of conductor elements when the flight object is docked to the charging device.
KR1020150133590A 2015-09-22 2015-09-22 Drone and charging system comprising for drone KR101768325B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
KR1020150133590A KR101768325B1 (en) 2015-09-22 2015-09-22 Drone and charging system comprising for drone

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
KR1020150133590A KR101768325B1 (en) 2015-09-22 2015-09-22 Drone and charging system comprising for drone

Publications (2)

Publication Number Publication Date
KR20170035042A KR20170035042A (en) 2017-03-30
KR101768325B1 true KR101768325B1 (en) 2017-08-17

Family

ID=58503113

Family Applications (1)

Application Number Title Priority Date Filing Date
KR1020150133590A KR101768325B1 (en) 2015-09-22 2015-09-22 Drone and charging system comprising for drone

Country Status (1)

Country Link
KR (1) KR101768325B1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021261658A1 (en) * 2020-06-22 2021-12-30 (주)아르고스다인 Charging connection device for drone
KR20220048529A (en) * 2020-10-12 2022-04-20 주식회사 이스온 Contact type charging system for drone

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106982813A (en) * 2017-04-26 2017-07-28 南京信息工程大学 A kind of fog machine independently fills agricultural chemicals device
CN108791054B (en) * 2018-06-13 2020-06-09 青岛文达通科技股份有限公司 Intelligent automobile safety protection method and system based on big data analysis
KR102565618B1 (en) * 2020-11-19 2023-08-10 주식회사 하백소프트 Charging system for unmanned vehicles
KR102598609B1 (en) * 2021-03-11 2023-11-07 주식회사 이스온 Charging system for drone
KR102558610B1 (en) * 2021-07-29 2023-07-27 한국전력공사 Biomimetic type flight device

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR200467869Y1 (en) * 2012-01-17 2013-07-23 허철 Electric powered free flight plane

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR200467869Y1 (en) * 2012-01-17 2013-07-23 허철 Electric powered free flight plane

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2021261658A1 (en) * 2020-06-22 2021-12-30 (주)아르고스다인 Charging connection device for drone
KR20220048529A (en) * 2020-10-12 2022-04-20 주식회사 이스온 Contact type charging system for drone
KR102559336B1 (en) * 2020-10-12 2023-07-26 주식회사 이스온 Contact type charging system for drone

Also Published As

Publication number Publication date
KR20170035042A (en) 2017-03-30

Similar Documents

Publication Publication Date Title
KR101768325B1 (en) Drone and charging system comprising for drone
CN204068303U (en) A kind of charging system, electric supply installation and aircraft
CN205051397U (en) Unmanned aerial vehicle is charging device independently
KR20140078251A (en) Charging equipment of flight vehicle and charging method
CN109361252A (en) A kind of protection circuit, battery and aircraft
CN109148758A (en) High-tension battery group and its assemble method
CN216672012U (en) Battery end electric connector with stable output, battery pack and electric automobile
US20220363410A1 (en) Universal aerial power supply system for a tethered small unmanned aerial vehicle
CN106218873A (en) The anti-protection structure of crashing of a kind of unmanned plane
CN103754373A (en) Wired power multiple rotor wing unmanned aerial vehicle
CN209282528U (en) A kind of docking facilities to charge in the air for aircraft
CN110100504B (en) Lightning arresting lightning arrester
CN211567686U (en) Carrying electric aircraft
CN212980523U (en) Undercarriage with buffering function for unmanned aerial vehicle
US20130335887A1 (en) Resistor, method of assembling the same, and switchgear
KR20200140032A (en) Charging system for drone
CN208637494U (en) Power supply module
KR102393330B1 (en) Drone apparatus
WO2022271136A1 (en) Contact and autonomous charging system for unmanned aerial vehicles
CN113928144A (en) Mobile unmanned aerial vehicle take-off and landing platform and take-off and landing control method
CN205872434U (en) Unmanned aerial vehicle fuselage protector
CN209448450U (en) A kind of protection circuit, battery and aircraft
US20210329803A1 (en) Adaptive Transceiver Power Supply
CN207993598U (en) A kind of high pressure cross connection type GIS arresters
CN110920432A (en) Unmanned aerial vehicle parking device and unmanned aerial vehicle adapted to same

Legal Events

Date Code Title Description
A201 Request for examination
E902 Notification of reason for refusal
E90F Notification of reason for final refusal
E701 Decision to grant or registration of patent right
GRNT Written decision to grant